A method for forming a solar panel can include attaching one or more tacking pads to one or both of a first surface of a first solar panel subassembly and a second surface of a second solar panel subassembly. The method further includes dispensing an adhesive onto at least one of the first and second surfaces. The first and second surfaces are placed in contact with the one or more tacking pads, thereby tacking the first and second solar panel subassemblies together, during which the first and second surfaces contact the adhesive, thereby decreasing a thickness and increasing a surface area of the adhesive. Subsequently, the adhesive is cured. The tacking pad(s) maintain fixed alignment of the solar panel subassemblies during curing of the adhesive, and establish a bond line of the adhesive.

An apparatus for assembling a securing tape on a trim strip to provide a trim cap structure having a base with an assembly path, a spool assembly to dispense tape from a coil, a guide assembly to guide the strip, and an applicator assembly to guide the securing tape to the portion of the trim strip on the assembly path. A method for assembling a sign component for a sign is also disclosed.

Apparatus and methods are described including an additional lens (24) made from an amorphous viscoelastic material and having an optical design. A curvature of the additional lens (24) is changed such as to conform with a curvature of abase eyeglasses lens (22), without causing a loss of the optical design of the additional lens (24), by heating the additional lens (24) to a temperature at which a Tan Delta of the amorphous viscoelastic material is between 0.2 and 0.8, and shaping the additional lens (24). Subsequently, the additional lens (24) is adhered to the base eyeglasses lens (22). The optical design of the additional lens (24) is such that, upon being adhered to the base eyeglasses lens (22), the adhered base eyeglasses lens (22) and the additional lens (24) provide a combined lens (20) having a desired optical prescription. Other applications are also described.

A method for welding thermoplastic components, in particular, thermoplastic fiber composite structural components for an aircraft or spacecraft, having the following steps. Arranging an insert, which has a conductor structure having a plurality of parallel electrical conductor elements, in a joining zone between a first thermoplastic component and a second thermoplastic component such that at least some portions of the parallel electrical conductor elements are located in the joining zone; locally melting the components in the region of the joining zone by supplying current to the conductor structure; disconnecting the connector elements; and removing the insert from the joining zone by pulling out the disconnected conductor elements. An insert for the resistance welding of thermoplastic components is also provided.

A method for joining two objects by anchoring an insert portion provided on one of the objects in an opening provided on the other one of the objects. The anchorage is achieved by liquefaction of a thermoplastic material and interpenetration of the liquefied material and a penetrable material, the two materials being arranged on opposite surfaces of the insert portion and the wall of the opening. Before such liquefaction and interpenetration, an interference fit is established in which such opposite surfaces are pressed against each other, and, for the anchoring, mechanical vibration energy and possibly a shearing force are applied, wherein the shearing force puts a shear stress on the interference fit.

A method for bonding composite substrates includes coupling a first co-cure prepreg layer having a first off-set amine to epoxide molar ratio onto a surface of a first composite substrate and coupling a second co-cure prepreg layer having a second off-set amine to epoxide molar ratio onto a surface of a second composite substrate. The first and second composite substrates are cured to the first and second co-cure prepreg layers, respectively, using a first cure cycle (including B-stage and cure temperatures) to form a first and a second co-cure prepreg layer portion. The method further includes coupling the first co-cure prepreg layer portion to the second co-cure prepreg layer portion and applying a second cure cycle to cure the first co-cure prepreg layer portion of the first composite substrate to the second co-cure prepreg layer portion of the second composite substrate to form a monolithic covalently bonded composite structure.

A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.

Disclosed is a method of resistance welding between composite articles. A conductive element is provided between faying surfaces, having a plurality of lower resistivity electrode portions spaced apart along the length of the contact area between the composite articles. The electrode portions can be used to spot weld across the electrode portions, and along a longitudinal portion of the conductive element between the electrode portions by application of an electrical current. Also disclosed are apparatus for use in the resistance welding methods and composite articles and structures and elements incorporating the conductive element.

A high altitude balloon, including a method and machine for manufacture, uses a perimeter border strip to couple two circular balloon panels with a lap or butt seal. Simultaneous sealing of two perimeter seals, one between the border strip and each of two balloon panels, is provided by supporting stacked balloon panels on a rotatable support and sealing around the full perimeter of the two interposed balloon panels and the border strip. The method and machine for manufacture allow for the mass production of high altitude balloons and minimize necessary material handling. The perimeter border strip can be dispensed and guided relative to the perimeter of the balloon panels for positioning before sealing together, as a bonding device is rotated relative to the balloon envelope.

A method for joining structural elements to a component made of at least one fiber-reinforced plastics material, includes providing at least two structural elements made of at least one fiber-reinforced plastics material having a particular matrix; providing at least one film element made of a thermoplastic heavy-duty material; arranging the at least one film element on a surface of one of the structural elements or between surfaces to be joined of the at least two structural elements to be joined; and producing the component to be joined in a curing process.